DescriptionThe goal of this study is to assess CFD capability for prediction of laminar shock wave/ boundary layer interactions at hypersonic velocities. More speci cally, the ow eld over a double cone con guration is simulated using perfect gas assumptions and Navier- Stokes equations. Computations are compared with experimental data obtained from measurements conducted in the LENS XX shock tunnel at CUBRC. Four separate cases of freestream conditions are simulated to examine the numerical methods in a wide range of enthalpies. The results of this investigation can provide factors for design optimization of hypersonic air vehicles. ii